KR20160122839A - Annular turbine engine combustion chamber - Google Patents

Abstract

The present invention relates to an annular turbine engine combustion chamber having an axial direction (X), a radial direction, and an azimuthal direction. The combustion chamber includes a first annular wall (12) and a second annular wall (14). Each wall defines at least a portion of the enclosure of the annular combustion chamber. The first and second walls 12, 14 have complementary interlocking elements 12d, 14d. The first wall 12 has at least one first through-hole 12f, while the second wall 14 has at least one second through-hole 14f. Further, the combustion chamber includes at least one pin inserted into the pair of holes including the first hole 12f and the second hole 14f. The pin 18 is formed by an injector and fixedly interconnects the first and second walls 12,14.

Description

{ANNULAR TURBINE ENGINE COMBUSTION CHAMBER}

The present invention relates to the field of turbo machine combustion chambers, and more particularly to turbo machines and, more particularly, to the field of toroidal combustion chambers for helicopter turboshaft engines that are not exclusive.

The term "turbomachine" is used to refer to any gas turbine device that generates drive output, and more particularly to a turboshaft engine in which the drive output is transmitted by rotating the drive shaft, and as a reaction to jetting high- And turbojets that provide the thrust required for propulsion. For example, turboshaft engines are used as engines in helicopters, ships, trains, and indeed as industrial power plants. TurboProp (turbo shaft engine that drives the propeller) is a turbo shaft engine used as an aircraft engine in the same way.

Conventional annular combustion chambers for turbo machines provide axial, radial, and azimuthal directions, generally including five annular walls, each annular wall defining at least a portion of the combustion chamber volume.

These annular walls are conventionally assembled together by welding or bolting. Assembling them together by welding makes it impossible to separate the first wall from the second wall, for example, for the purpose of replacing one of the walls or for maintenance. Assembly by screw tightening causes cracks to appear in the vicinity of the holes to which the bolts are joined due to the resulting blocking, thereby providing a drawback of weakening the combustion chamber. Also, assembling in this manner is complex, time consuming, and expensive.

One embodiment provides an annular combustion chamber for a turbomachine that provides axial, radial, and azimuthal directions, and includes a first annular wall and a second annular wall, each wall having at least a portion of the volume of the annular combustion chamber Wherein the first and second walls provide a complementary fitting element wherein the first wall provides at least one first through hole while the second wall defines at least one second through hole Wherein the combustion chamber also has at least one pin coupled to a pair of holes including a first hole and a second hole, wherein the pin locks the fittings of the first and second walls.

The first annular wall has a first fitting element, the second annular wall has a second fitting element, and the first and second fitting elements are connected to each other to cooperate by fitting in the axial and / or azimuthal direction of the combustion chamber, Lt; / RTI > In other words, the first and second fitting elements are fitted or joined together by moving them relative to each other along the axial and / or azimuthal direction of the combustion chamber.

The combustion chamber may have two or more annular walls. With three or more walls, the assembly of the plurality of annular walls can be locked by the pins. For example, a single pin may lock at least three (or more than four) distinct wall assemblies together. In another embodiment, the fins may lock the assembly of the two walls, i.e., the first wall and the second wall, and the other fins lock the assembly of the first and second walls and the third wall together.

It can be appreciated that the first wall provides one or more first holes and the second wall provides one or more second holes. Of course, in a variant, there are as many first holes as there are second holes, and each first hole is paired (or vice versa) with the second hole. In the following, unless otherwise specified, the terms "first hole" and "second hole " designate only one first hole or first hole or only one second hole or second hole.

The combustion chamber has one or more fins. In the following, unless stated otherwise, the term "pin" is used to denote only one pin or both pins. By way of example, the pin may be a rod or a clip configured to be simultaneously coupled to a first hole and a second hole forming a pair of holes. The pins are coupled such that there is or is not a gap in the pair comprising the first hole and the second hole. These fins cooperate only by coupling with a fitting or hole in a pair of holes to allow the first and second walls to rotate in one or more degrees of freedom, for example axial translation and / or rotation about the axial direction of the combustion chamber They combine with one another about motion, but nevertheless do not block all degrees of freedom. These fins can avoid or significantly reduce the risk of cracking as compared to the use of conventional bolts. This pin thus enables the walls of the combustion chamber to be assembled together without any need for clamping and / or welding the two walls to one another, as is done in a conventional combustion chamber.

Naturally, when the combustion chamber provides a plurality of pairs of first and second holes, the combustion chamber may provide a plurality of fins, and each of the fins is coupled to a pair of holes. In a variation, when a pin is provided in a pair of holes, the pair of holes receives a single pin. In a variant, there are as many pins as there are pairs of first and second holes. In a variant, the pins are similar.

The pin prevents relative movement in the axial direction and / or the azimuthal angle between the first and second walls. Thus, when the pin is coupled to the hole pair (s), the fitting between the first and second walls is locked. In order to separate the first and second walls from each other, it is necessary to start by removing the pin (s) from the first and second hole pair (s).

Thus, the combustion chamber can be assembled easily, quickly, and at low cost, without requiring a welding operation, and compared with combustion chambers of the prior art. Further, such a combustion chamber can likewise be easily disassembled, thus facilitating the maintenance work.

In some embodiments, the first hole and the second hole of the pair of holes are arranged to be substantially opposed to each other.

It is also to be understood that the term "opposite" is used to mean that the first hole is aligned with the second hole in the axial direction and azimuthally to provide the same angular position. In other words, the first and second holes of the pair of holes are not diametrically opposite. This opposing configuration makes it possible to use a simple pin, making it easy to assemble and to be effective.

In certain embodiments, the fins may be formed by an injector.

Of course, the combustion chamber may provide other pins formed by other components. In a variant, the combustion chamber may provide a plurality of fins, and each fin may be formed by an injector.

Using an injector as a pin leads to savings in weight for the combustion chamber, and saving weight is a major concern in turbo machines used in aviation. This also simplifies the structure of the combustion chamber, which can contribute to facilitating assembly and / or disassembly. Further, by using the injector as a pin, it is possible to fix and position the combustion chamber directly in the turbo machine in this manner.

In certain embodiments, the fins extend substantially radially.

The term "substantially radial" is used to mean an angle forming an angle in the range of 60 [deg.] To 120 [deg.] With respect to the axis of the combustion chamber and a direction parallel to the radial plane.

This orientation to the pin (s) serves to facilitate assembly of the combustion chamber, and the locking of the fitting is even more suitable.

In certain embodiments, the complementary fitting element comprises a plurality of axial tongues extending from one of the first and second walls, and a plurality of apertures provided in the other of the first and second walls, The opening accommodates the tongue. Under such circumstances, the complementary fitting element forms a complementary element for the axial fitting.

It can be appreciated that the first wall and / or the second wall have one or more tongues. Thus, the first wall may provide tongue, while the second wall may not provide any tongue, and the first wall may not provide any tongue, while the second wall may provide tongue, Or in fact the first wall may provide a plurality of first tongue portions while the second wall provides a plurality of second tongue portions.

The other wall has an opening that is arranged to face the tongue and can accommodate the tongue and cooperate with the tongue by axial fitting. Thus, if only the first wall provides a tongue, the second wall provides an opening, and if only the second wall provides the tongue, the first wall provides an opening, whereas if the first wall is the first tongue, And the second wall provides a second tongue, the first wall provides a first opening for receiving the second tongue and the second wall provides a second opening for receiving the first tongue.

In a variant, the tongue and the opening are regularly distributed (or spaced) at the azimuth angle. Thus, it can be appreciated that the angular space between adjacent tongues and adjacent openings is the same. This distribution makes it possible to obtain a degree of rotational symmetry for the complementary fitting elements, thus facilitating the operation of fitting the walls together and thus of assembling the combustion chamber.

In certain embodiments, a hole in one of the first and second walls is provided in the protruding blade.

If the hole is the first hole, it can be understood that the blade is a protruding portion from the first wall, or if the hole is the second hole, the blade is a protruding portion from the second wall. This arrangement enables to reduce the weight of the wall while reducing the overall size of the combustion chamber in the vicinity of the blades. This configuration also makes it possible to define the position of the hole to a specific position that is well controlled within the combustion chamber, thereby reducing any risk of adverse outflow from the perspective of the performance of the combustion chamber.

In some embodiments, protrusions disposed in adjacent ones of the other holes of the first hole and the second hole extend substantially parallel to the axis of the other hole and cooperate with the blade by snap-fitting.

For example, the proximal portion of the hole includes an annular portion of the wall that extends around the hole beyond three times the diameter (or maximum dimension) of the hole. For example, the protrusions are formed by protrusions that are machined directly on the walls, e.g., by die-stamping, or by separate parts that are secured to the walls.

Snap-fitting (or clipping) is a technique for assembling the two parts together by elastic deformation and mutual coupling (typically by deforming both the local deformation of the blade, or all of the parts involved in the assembly, for example) to be. When the two parts are joined at the snap-fitting position, they are generally returned to their initial shape and no longer provide elastic deformation (or they provide a smaller elastic deformation). When the two parts are engaged with each other at the snap-fitting position, they cooperate with each other to block or actually prevent relative movement between the parts in the separating direction (direction opposite to the engaging direction). In the snap-fitting position, the two portions can also cooperate in a manner that resists or actually prevents relative motion between them in a direction to extend the engagement beyond the snap-fitting position.

This snap-fit allows the first and second walls to be held in the fitted position before locking the fitting using the pin.

In some embodiments, the boundaries of the other holes form protrusions that extend substantially parallel to the axis of the other holes to cooperate with the blades by snap-fitting.

In certain embodiments, a wall of one of the first wall and the second wall provides an axial annular shoulder that cooperates in contact with the other of the first wall and the second wall.

Such a shoulder forms a connection plane between the first and second walls to enable the outflow from within the combustion chamber to be minimized or reduced to zero.

In some embodiments, the combustion chamber has only two annular walls, i.e., a first annular wall and a second annular wall, which define the volume of the combustion chamber.

The first and second walls are thus sufficient to independently define the volume of the combustion chamber. These combustion chambers provide a particularly small number of walls and thus make it easier, faster, and less expensive to assemble. Also, disassembly for maintenance purposes is also easier. In addition, the combustion chamber providing such a small number of walls provides a lower risk of outflow, especially in the vicinity of the connection between the various walls.

Embodiments provide a turbo machine including a combustion chamber according to any of the embodiments described in this description.

The invention and its advantages can be better understood when reading the following detailed description of various embodiments of the invention given as non-limiting examples. This description refers to the accompanying drawing sheet, wherein:
1 shows a turbo machine with a combustion chamber;
Figure 2 shows a perspective view of the annular wall of the combustion chamber of Figure 1;
Figure 3 is a detail view of the annular wall of Figure 1; And
Figure 4 shows the annular wall of Figure 1 assembled together.

Figure 1 shows a turbo machine 100 having an annular combustion chamber 10 while Figures 2 to 4 show two annular walls 12 and 14 of the combustion chamber 10 in more detail. Although the combustion chamber 10 is a reverse flow type annular chamber, it should be noted that the present invention is not limited to this particular type of combustion chamber.

The combustion chamber 10 provides axial, radial (R), and azimuthal directions (along the axis X). The combustion chamber (10) provides rotational symmetry about an axis (X). In this embodiment, the first wall 12 forms a flame tube that defines the volume at which fuel is ignited, i.e., where combustion occurs. The second wall 14 forms an outer bend and serves as a deflector for guiding the gas flow from the flame tube. This combustion chamber embodiment 10 has only two annular walls 12 and 14 for defining the volume 10a of the combustion chamber 10. [

More specifically, each of the first wall 12 and the second wall 14 provides an overall shape that is substantially one-half of the torus, which, like a donut mold, is perpendicular to the axis of rotation of the x torus And the two half-toruses are arranged to face each other. Each of the walls 12 and 14 thus has a substantially axially outer portion 12a and 14a and a substantially axially inner portion 12b and 14b and an outer portion 12a of the first wall 12, And a bottom 12c or 14c connecting the inner portion 12b with the inner portion 12b or connecting the outer portion 14a and the inner portion 14b of the second wall 14 to each other. Generally, and unless otherwise specified, the adjectives "inner" and "outer" are intended to mean that the inner portion (i.e., the radially inner portion) of the component is less than the outer portion It should be recalled that it is used with reference to the radial direction so that it is closer to the axis X.

In this embodiment, the radius of the outer portion 12a of the first wall 12 is substantially the same as the radius of the outer portion 14a of the second wall 14, The radius of the inner portion 12b of the second wall 14 is larger than the radius 14b of the second wall 14. [ It is thus possible to assemble the first wall 12 through the second wall 14 and the outer walls 12a and 14a thereof and the outer portion 12a of the first wall 21 to the second wall 14, while the difference in radii of the inner portions 12b, 14b serves to create an exhaust duct for the combustion gases.

The first wall 12 provides a plurality of axial tongues 12d while the second wall 14 includes a plurality of openings 14d configured to receive the tongue 12d of the first wall 12 ). In this embodiment, the tongue 12d and the opening 14d form a complementary axial fitting element of the first and second walls 12 and 14. Of course, in a variation not shown, the tongue may form a complementary element for fitting with azimuthal angle, or with both axial and azimuthal angles.

The axial tongue portion 12d extends axially from the outer portion 12a of the first wall 12. The opening 14d is arranged in an annular shoulder 14e which extends in the radial direction and connects the outer portion 14a to the bottom 14c of the second wall 14. In this embodiment, there are as many tongues 12d as there are openings 14d, and each opening 14d receives one tongue 12d.

When the first wall 12 is axially fitted with the second wall 14 the tongue 12d is allowed to penetrate through the opening 14d while the axial free end of the outer portion 12a of the first wall Cooperate by axial contact with shoulder 14e.

The first wall 12 provides a plurality of first through holes 12f, the axis of which extends radially. The holes 12f are arranged in the outer portion 12a of the wall 12. The second wall 14 provides a second through-hole 14f having an axis extending in the radial direction. The holes 14f are arranged in blades 14g that protrude axially from the outer portion 14a of the second wall 14. In this embodiment, the holes 12f and 14f are substantially circular, but they may, of course, provide some other shape. When the first and second walls 12 and 14 are fitted, the holes 12f and 14f face each other. In this embodiment, there are as many first holes 12f as there are second holes 14f.

The sleeve 16 configured to receive the injector 18 is secured to each first hole 12f by, for example, welding or crimping. The sleeve 16 forms a boundary protruding outward along the axis of each first hole 12f. The maximum radius of the sleeve 16 is smaller than the radius of the second hole 14f. Thus, during fitting of the first and second walls 12 and 14, each blade 14g cooperates by snap-fitting with the sleeve 16.

After the first and second walls 12 and 14 have been fitted, the rim 20 is positioned on the outer side of the first wall 12, in order to block the blade 14g snap- (12a). By way of example, the rim 20 is welded. These rims 20 form the fins for locking the fittings and provide a mid closure of the fittings of the walls 12 and 14 before mounting of the injector 18 described below. More than one rim may be provided. In this embodiment, there are as many rims 20 as there are blades 14g. Of course, this rim 20 is optional, and thus they may be omitted in some combustion chamber variants.

When the first and second walls 12 and 14 are axially fitted, the first hole 12f faces the second hole 14f. Next, the inlet jaw 18 is inserted into each of the opposing pair of first and second holes 12f and 14f, and the injector has a pin for locking the fittings of the first and second walls 12 and 14 . The injector 18 extends radially through each pair of holes 12f and 14f. The injector 18 is coupled with a gap in each pair of holes to allow relative movement between each of the components due to the different thermal expansion, but nevertheless the injector has translational and azimuthal angles along the axial direction X Coupling the first and second walls 12 and 14 together in rotational motion in the direction Y. [ Of course, the sleeve 16 also contributes to coupling the first and second walls 12 and 14 to one another, but this coupling is particularly advantageous under certain circumstances where the blade 14g effectively cooperates with the sleeve 16 Despite the rim 20, it is relatively fragile due to the difference in thermal expansion that can stop it. Thus, an essential part of the locking of the fitting between the first and second walls 12 and 14 is formed by the fin formed by the injector 18. [

Although the present invention has been described with reference to particular embodiments, it is evident that modifications and variations may be made to these embodiments without departing from the overall scope of the invention as defined by the claims. In particular, individual features of the various embodiments shown and / or referred to may be combined in additional embodiments. Consequently, the description and drawings are to be regarded as illustrative rather than restrictive.

Claims (9)

(10) for a turbomachine (100) comprising a first annular wall (12) and a second annular wall (14) and providing an axial direction (X), a radial direction Each wall defining at least a portion of the volume 10a of the annular combustion chamber 10 and the first and second walls 12 and 14 having complementary fitting elements 12d, Wherein the first wall (12) provides at least one first through-hole (12f) while the second wall (14) provides at least one second through-hole (14f) , Wherein the combustion chamber (10) further comprises at least one pin (18) coupled to a pair of holes including a first hole (12f) and a second hole (14f), the pin (18) And locking the fitting of the second wall (12, 14), said pin being formed by an injector (18). 2. The combustion chamber (10) according to claim 1, wherein the first hole (12f) and the second hole (14f) of the pair of holes are disposed substantially opposite to each other. The combustion chamber (10) according to claim 1 or 2, wherein the pin (18) extends substantially radially. The device of any one of claims 1 to 3, wherein the complementary fitting element comprises a plurality of axial tongue portions (12d) extending from a wall of one of the first wall (12) and the second wall (14) And a plurality of openings (14d) provided in the remaining one of the first wall (12) and the second wall (14), wherein the opening (14d) includes a tongue (12d) . The combustion chamber (10) according to any one of claims 1 to 4, wherein one of the first hole (12f) and the second hole (14f) is provided in a protruding blade (14g). 6. The apparatus according to claim 5, wherein a protrusion (16) arranged in the periphery of the remaining one of the first hole (12f) and the second hole (14f) extends substantially parallel to the axis of the remaining hole, (14g). ≪ / RTI > 7. A device according to any one of the preceding claims, characterized in that a wall of one of the first wall (12) and the second wall (14) is located between the first wall (12) To provide an annular shoulder (14e) in axial axial contact with and cooperating therewith. 8. A method according to any one of claims 1 to 7, wherein only two annular walls defining the volume (10a) of the combustion chamber (10), i.e., the first annular wall (12) and the second annular wall (10). A turbo machine (100) comprising a combustion chamber (10) according to one of claims 1 to 8.

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